CN108622436A - A kind of repair method after composite material blade damage - Google Patents
A kind of repair method after composite material blade damage Download PDFInfo
- Publication number
- CN108622436A CN108622436A CN201810650891.3A CN201810650891A CN108622436A CN 108622436 A CN108622436 A CN 108622436A CN 201810650891 A CN201810650891 A CN 201810650891A CN 108622436 A CN108622436 A CN 108622436A
- Authority
- CN
- China
- Prior art keywords
- blade
- composite material
- repair
- prepreg
- covering
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/40—Maintaining or repairing aircraft
Abstract
A kind of repair method after being damaged the present invention provides composite material blade.Clean blade covering damage field surface；Polishing removal blade covering damage field and foam core damage field；It processes covering and repairs area step type face；Filler repairing is carried out to foam core damage field；Area step type face cuts the prepreg of different size, direction, type, the lay of row order of going forward side by side ladder cloth；Temperature-pressure cures；The present invention is overlapped mutually reinforcement using different layers of prepreg ladder cloth, and completes composite material blade covering damage repair in the temperature, pressure of composite material blade regional area offer stable and uniform using special instrument repair apparatus of vulcanizing.The present invention can complete composite material blade covering damage repair in high quality with high efficiency, and covering is effectively ensured and repairs intensity, reduces blade scrappage, shortens the blade repair cycle, improve the service life of blade.
Description
Technical field
Behind composite rotor blade service technique field more particularly to a kind of damage of composite material blade
Repair method.
Background technology
Covering is the important Parts in composite material blade structure, and the torsion stiffness and shimmy stiffness contribution to blade are very
Greatly, it is made of preimpregnate glass cloth and the preimpregnation common paving of carbon cloth.Composite material blade is in transport, management process, often
There is a situation where coverings by gouge, and some even injures the foam core below covering, to paddle blade structure intensity, fatigue life and
Flight safety influences very big.Traditional method is to carry out encapsulating repairing using cold setting adhesive.Its advantage is that it is simple and practicable,
But for disadvantage it is also obvious that being easy unsticking for a long time, repairing effect is poor.
Invention content
In view of the problems of the existing technology, the purpose of the present invention is to provide a kind of reliable and stable composite material blades
Covering repair method.
Technical solution：To achieve the above object, the present invention provides the repair method after a kind of damage of composite material blade, packet
Include following steps：
The first step, cleaning blade damage field, centered on blade core damage field, by the multilayer outside blade core
Covering is cut into the hierarchic structure of diffusion type so that it is bigger that the covering of more outer layer cuts rear exposed area；
Second step, filling and repairing blade core damage field；
Third step, paving repair prepreg in region exposed after each layer covering is cut so that the hierarchic structure of diffusion type
Successively tamped；
Step 4: carrying out temperature-pressure to damage field so that repair prepreg cures；
Step 5: polishing the damage field after solidification.
Further, before step 4, the paving glass cloth outside outermost repair prepreg.
Further, the repair prepreg is carbon cloth prepreg.
Further, in step 3, the paving angle between adjacent repair prepreg is interlocked.
Further, the plan view shape of the hierarchic structure of the diffusion type is rectangle or circle.
Further, the ladder width of the hierarchic structure of the diffusion type is 10-15mm.
Advantageous effect
Covering can be effectively ensured using the method for the present invention and repair intensity, meet blade theory shape requirement, improve and repair
Quality and working efficiency.
Description of the drawings
Fig. 1 is each layer paving schematic diagram；
Wherein：1- innermost layers prepreg, 2- middle layers prepreg, 3- middle layers prepreg, 4- outermost layers prepreg, a- are most
Internal layer covering, b- middle layers covering, c- outermost layer coverings.
Specific implementation mode
Below in conjunction with the accompanying drawings, the present invention is made a more thorough explanation, shown in the drawings of the exemplary implementation of the present invention
Example.Repair method after a kind of damage of composite material blade, includes the following steps：
The first step, cleaning blade damage field, centered on blade core damage field, by the multilayer outside blade core
Covering is cut into the hierarchic structure of diffusion type so that it is bigger that the covering of more outer layer cuts rear exposed area；
Second step, filling and repairing blade core damage field；
Third step, paving repair prepreg in region exposed after each layer covering is cut so that the hierarchic structure of diffusion type
Successively tamped；
Step 4: carrying out temperature-pressure to damage field so that repair prepreg cures；
Step 5: polishing the damage field after solidification.
Further, before step 4, the paving glass cloth outside outermost repair prepreg.
Further, the repair prepreg is carbon cloth prepreg.
Further, in step 3, the paving angle between adjacent repair prepreg is interlocked.
Another embodiment：The first step：Clean blade covering damage field surface；Second step：The blade of polishing removal damage
Covering and foam core；Third walks：It processes covering and repairs area step type face, ladder width is generally 10-15mm；4th step：It is right
Foam core damage field carries out filler repairing；5th step：Different size, direction, type are cut according to area step type face is repaired
Prepreg, the lay of row order of going forward side by side ladder cloth；6th step：Instrument is vulcanized in installation, makes vacuum system, temperature-pressure solidification.；7th
Step：The glue tumor for clearing up blade surface, polishes smooth, and local frictioning is repaired.
Claims (6)
1. the repair method after a kind of composite material blade damage, includes the following steps：
The first step, cleaning blade damage field, centered on blade core damage field, by the multi-layer covering outside blade core
It is cut into the hierarchic structure of diffusion type so that it is bigger that the covering of more outer layer cuts rear exposed area；
Second step, filling and repairing blade core damage field；
Third step, paving repair prepreg in region exposed after each layer covering is cut so that the hierarchic structure of diffusion type by by
Layer tamps；
Step 4: carrying out temperature-pressure to damage field so that repair prepreg cures；
Step 5: polishing the damage field after solidification.
2. the repair method after a kind of composite material blade damage according to claim 1, it is characterised in that：Step 4 it
Before, the paving glass cloth outside outermost repair prepreg.
3. the repair method after a kind of composite material blade damage according to claim 1, it is characterised in that：The repairing
Prepreg is carbon cloth prepreg.
4. the repair method after a kind of composite material blade damage according to claim 1, it is characterised in that：Step 3
In, the paving angle between adjacent repair prepreg is interlocked.
5. the repair method after a kind of composite material blade damage according to claim 1, it is characterised in that：The expansion
The plan view shape for dissipating the hierarchic structure of formula is rectangle or circle.
6. the repair method after a kind of composite material blade damage according to claim 1, it is characterised in that：The expansion
The ladder width for dissipating the hierarchic structure of formula is 10-15mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810650891.3A CN108622436A (en) | 2018-06-22 | 2018-06-22 | A kind of repair method after composite material blade damage |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810650891.3A CN108622436A (en) | 2018-06-22 | 2018-06-22 | A kind of repair method after composite material blade damage |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108622436A true CN108622436A (en) | 2018-10-09 |
Family
ID=63692118
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810650891.3A Pending CN108622436A (en) | 2018-06-22 | 2018-06-22 | A kind of repair method after composite material blade damage |
Country Status (1)
| Country | Link |
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| CN (1) | CN108622436A (en) |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109592070A (en) * | 2018-10-12 | 2019-04-09 | 江西昌河航空工业有限公司 | A kind of replacing options of composite material blade trimmer |
| CN110125606A (en) * | 2019-03-22 | 2019-08-16 | 中国人民解放军海军航空大学青岛校区 | A kind of metal structure holes damaged composite material bonding repair method |
| CN110182383A (en) * | 2019-05-17 | 2019-08-30 | 陕西飞机工业（集团）有限公司 | A kind of solution of metal skin sandwich part covering bulge failure |
| CN110877464A (en) * | 2019-09-25 | 2020-03-13 | 西北工业大学 | Standard hard patching method for rapid repair of aircraft composite materials |
| CN113734462A (en) * | 2021-06-10 | 2021-12-03 | 江苏航空职业技术学院 | Skin maintenance method for sports aircraft |
| CN113942657A (en) * | 2021-10-09 | 2022-01-18 | 中国直升机设计研究所 | Composite material blade trailing edge and blade tip trailing edge gouge repairing method |
| CN114211785A (en) * | 2021-12-13 | 2022-03-22 | 沈阳航空航天大学 | Composite material repairing process for aircraft skin hole-breaking type damage |
| CN114368173A (en) * | 2021-11-24 | 2022-04-19 | 中国南方航空股份有限公司 | Typical gradual change step type hyperbolic laminate structure penetrating damage repair process |
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| CN105313351A (en) * | 2014-07-08 | 2016-02-10 | 哈尔滨飞机工业集团有限责任公司 | Helicopter main blade trailing edge shrinking cloth repairing method |
| US20160137316A1 (en) * | 2014-11-13 | 2016-05-19 | Mitsubishi Aircraft Corporation | Method for locating machining position in repair material, and repairing method |
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Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109592070A (en) * | 2018-10-12 | 2019-04-09 | 江西昌河航空工业有限公司 | A kind of replacing options of composite material blade trimmer |
| CN110125606A (en) * | 2019-03-22 | 2019-08-16 | 中国人民解放军海军航空大学青岛校区 | A kind of metal structure holes damaged composite material bonding repair method |
| CN110182383A (en) * | 2019-05-17 | 2019-08-30 | 陕西飞机工业（集团）有限公司 | A kind of solution of metal skin sandwich part covering bulge failure |
| CN110877464A (en) * | 2019-09-25 | 2020-03-13 | 西北工业大学 | Standard hard patching method for rapid repair of aircraft composite materials |
| CN113734462A (en) * | 2021-06-10 | 2021-12-03 | 江苏航空职业技术学院 | Skin maintenance method for sports aircraft |
| CN113734462B (en) * | 2021-06-10 | 2023-08-15 | 江苏航空职业技术学院 | Skin maintenance method for sports aircraft |
| CN113942657A (en) * | 2021-10-09 | 2022-01-18 | 中国直升机设计研究所 | Composite material blade trailing edge and blade tip trailing edge gouge repairing method |
| CN113942657B (en) * | 2021-10-09 | 2023-09-08 | 中国直升机设计研究所 | Repair method for rear edge and tip rear edge of composite blade |
| CN114368173A (en) * | 2021-11-24 | 2022-04-19 | 中国南方航空股份有限公司 | Typical gradual change step type hyperbolic laminate structure penetrating damage repair process |
| CN114368173B (en) * | 2021-11-24 | 2023-07-07 | 中国南方航空股份有限公司 | Typical gradual change step type hyperbolic laminate structure penetrating damage repair process |
| CN114211785A (en) * | 2021-12-13 | 2022-03-22 | 沈阳航空航天大学 | Composite material repairing process for aircraft skin hole-breaking type damage |
| CN114211785B (en) * | 2021-12-13 | 2024-03-29 | 沈阳航空航天大学 | Composite material repairing process for aircraft skin hole type damage |
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Application publication date: 20181009 |